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Method for determining preliminary orbit of low-orbit target satellite according to space-based satellite angle measurement data

A technology for target stars and satellites, which is applied in the field of low-orbit target satellite angle measurement data to determine its initial orbit, and can solve problems that affect the accuracy of orbit determination

Active Publication Date: 2014-07-16
SHANGHAI ENG CENT FOR MICROSATELLITES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In view of the problem that the existing space-based technology for determining the target orbit of low-orbit satellites will automatically converge to the vicinity of the false solution, which seriously affects the accuracy of orbit determination, the purpose of the present invention is to provide a method for determining the initial orbit based on the relative observation star angle data of low-orbit target satellites. This method shields the traditional false solution of the initial orbit motion equation based on space-based angle measurement data, makes the program converge towards the true solution, and achieves higher orbit determination accuracy

Method used

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  • Method for determining preliminary orbit of low-orbit target satellite according to space-based satellite angle measurement data
  • Method for determining preliminary orbit of low-orbit target satellite according to space-based satellite angle measurement data
  • Method for determining preliminary orbit of low-orbit target satellite according to space-based satellite angle measurement data

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Embodiment 1

[0127] The orbital elements of the satellites are as follows:

[0128] a=7203.709km

[0129] i=80°

[0130] Ω=130.14°

[0131] e=0.00187

[0132] λ=M+ω=272.59°

[0133] ρ 0 =1526.9km

[0134] ρ min =635.4km

[0135] The angle measurement accuracy is 19 arc seconds, the data is 479 seconds, 240 points, one point every 2 seconds, the simulation results of the initial orbit accuracy and the relationship with the lower bound of C.R see image 3 .

Embodiment 2

[0137] The orbital elements of the target star are as follows:

[0138] a=7311.066km

[0139] i=70°

[0140] Ω=143.93°

[0141] e=0.0016

[0142] λ=M+ω=272.95°

[0143] ρ 0 =1840.2km

[0144] ρ min =1187.3km

[0145] The angle measurement accuracy is 19 arc seconds, the data is 258 seconds, 129 points, one point every 2 seconds, the simulation results of the initial orbit accuracy and the relationship with the lower bound of C.R see Figure 4 .

Embodiment 3

[0147] The orbital elements of the satellites are as follows:

[0148] a=7405.907km

[0149] i=70°

[0150] Ω=146.75°

[0151] e=0.00133

[0152] λ=M+ω=275.11°

[0153] ρ 0 =2241.6km

[0154] ρ min =1523.4km

[0155] The angle measurement accuracy is 19 arc seconds, the data is 281 seconds, 141 points, one point every 2 seconds, the simulation results of the initial orbit accuracy and the relationship with the lower bound of C.R see Figure 5 .

[0156] It can be seen from the simulation results that the solution provided by the present invention can converge the results of the calculation program near the true solution, and there is little difference from the theoretical optimal solution C.R lower bound, which fully proves the correctness and feasibility of this method.

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Abstract

The invention discloses a method for determining a preliminary orbit of a low-orbit target satellite according to space-based satellite angle measurement data. According to the method, a condition equation of the unit vector (please see the specification for the symbol) of the target satellite relative to an observation satellite is obtained according to the angle measurement data of the high-speed motion low-orbit target satellite relative to the low-orbit observation satellite; the condition equation of measured distance rho <0> (please see the specification for the formula) is obtained on the premise that the condition equation is constrained, and an iterative solution is obtained to serve as the initial values, position (please see the specification for the symbol) and speed (please see the specification for the symbol), of the next step of iteration by selecting a certain step length and adding certain weights to rho <0> in the constraint equation and the semi-major axis a <0> of the target satellite, then iterative calculation is conducted till convergence to obtain the preliminary orbit of the target satellite, spurious solutions are blocked out and a genuine solution is obtained, and then the position and speed of the target satellite are determined. According to the method, by attaching the constraint condition to the solution target, the generation of spurious solutions caused by the high-speed dynamic nature of the target satellite relative to the observation satellite and the lack of distance observed quantity is avoided, the calculation procedure is successfully converged to be close to the genuine solution, and an orbit determination result is made to be close to the lower bound of a theoretical optimum solution C.R.

Description

technical field [0001] The invention relates to the technical field of satellite initial orbit determination in the precise orbit determination of artificial satellites, in particular to a method for determining the initial orbit of a low-orbit target satellite based on angle measurement data of a low-orbit target satellite measured by an observation star. Background technique [0002] Determining the orbit of the low-orbit target satellite based on the angular measurement data of space-based satellites was initially considered to be no different from the initial orbit determination based on the angular measurement data of the ground-based observation station, and it was only to move the observation station from the ground to the sky. In fact, there is a big difference between the two. Ground-based stations only rotate with the earth, while observation satellites run at high speed in low-orbit orbits, and their mechanical laws of motion are very similar to those of low-orbit ...

Claims

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Application Information

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IPC IPC(8): G06F17/11
Inventor 吴会英周美江陈宏宇齐金玲
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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